Preliminary Flight Measurements Of The Total Pressure Recovery Of A Split Wing Ram Jet Inlet At Mach Numbers From 1 4 To 3 16
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| Author | : A. H. Hinners |
| Publisher | : BiblioGov |
| Total Pages | : 32 |
| Release | : 2013-07 |
| Genre | : |
| ISBN | : 9781289267643 |
The NASA Technical Reports Server (NTRS) houses half a million publications that are a valuable means of information to researchers, teachers, students, and the general public. These documents are all aerospace related with much scientific and technical information created or funded by NASA. Some types of documents include conference papers, research reports, meeting papers, journal articles and more. This is one of those documents.
| Author | : Leonard W. Putland |
| Publisher | : |
| Total Pages | : 30 |
| Release | : 1956 |
| Genre | : Boundary layer control |
| ISBN | : |
Two models each utilizing a scoop inlet located at the maximum-body-diameter station operating mass-flow ratios from 0.76 to 0.96 have been flight tested at an angle of attack of approximately zero degrees over a Mach number range from 0.8 to 1.8, and a Reynolds number range from 2,000,000 to7,000,000 based on body maximum diameter. One of the scoop inlets had a circular cross section with a boundary-layer diverter. The other scoop inlet had a semicircular cross section wrapped partly around the body with a boundary-layer splitter plate ahead of the inlet.
| Author | : Mikhail Makarovich Bondari͡u︡k |
| Publisher | : |
| Total Pages | : 466 |
| Release | : 1969 |
| Genre | : Airplanes |
| ISBN | : |
| Author | : John A. Zalovcik |
| Publisher | : |
| Total Pages | : 26 |
| Release | : 1944 |
| Genre | : Aerodynamic load |
| ISBN | : |
Summary: A flight investigation was made to compare static pressures in subsonic and supersonic flow over an airplane wing as measured by static-pressure tubes, a static-pressure belt, and orifices flush with the wing surface. The measurements were made on the upper surface of the wing of the P-47D airplane over a range of flight conditions in which local Mach numbers from 0.34 to 1.41 were obtained at the measurement stations. For some of the tests, a total-pressure tube was mounted on the wing surface to determine its characteristics in supersonic flow. The results indicated that static-pressure measurements obtained with suitably designed and installed flush orifices, static-pressure tubes, and static-pressure belt will be in reasonable agreement for both subsonic and supersonic flow. The pressures in supersonic flow measured by the total-pressure tube mounted on the wing surface were found to be in close agreement with values predicted by theory.
| Author | : R. I. Sears |
| Publisher | : |
| Total Pages | : 38 |
| Release | : 1951 |
| Genre | : Charts, diagrams, etc |
| ISBN | : |
An investigation has been made with rocket-propelled models in free flight to determine the external drag and pressure recovery of the NACA 1-40-250 nose inlet at zero angle of attack. The Mach number range of the tests was from 0.9 to 1.8 and the corresponding Reynolds numbers based on body diameter varied from 4,000,000 to 10,000,000. A technique was developed for varying the internal air flow during flight so that the drag and pressure-recovery characteristics were measured as functions of both mass-flow ratio and Mach number. A pointed parabolic-arc body having the same contour as that of the inlet model aft of the inlet region was also tested to serve as a basis for drag comparison.
| Author | : H. Herbert Jackson |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1960 |
| Genre | : Mach number |
| ISBN | : |
| Author | : Julio Chu |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1996 |
| Genre | : Angle of attack |
| ISBN | : |
| Author | : Peter W. Merlin |
| Publisher | : AIAA (American Institute of Aeronautics & Astronautics) |
| Total Pages | : 240 |
| Release | : 2008 |
| Genre | : History |
| ISBN | : |
The Lockheed Blackbirds hold a unique place in the development of aeronautics. In their day, the A-12, YF-12, M-21, D-21, and SR-71 variants outperformed all other jet airplanes in terms of altitude and speed. Now retired, they remain the only production aircraft capable of sustained Mach 3 cruise and operational altitudes above 80,000 feet.This is the first book to address the technical aspects of these incredible aircraft. The author describes the design evolution of the Blackbird, from the Archangel to the Senior Crown (the Air Force's SR-71.) He describes in detail the construction and materials challenges faced by Lockheed, as well as the Blackbird's performance characteristics and capabilities.A NASA historian, the author describes NASA's role in using the aircraft as a flying laboratory to collect data on materials, structures, loads, heating, aerodynamics, and performance for high-speed aircraft. The reader will benefit from the technical and programmatic lessons learned.This volume was produced in cooperation with the National Aeronautics and Space Administration.
| Author | : Harold Mirels |
| Publisher | : |
| Total Pages | : 28 |
| Release | : 1949 |
| Genre | : Aerodynamic load |
| ISBN | : |
An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.
| Author | : R. I. Sears |
| Publisher | : |
| Total Pages | : 30 |
| Release | : 1954 |
| Genre | : Noses (Aircraft) |
| ISBN | : |
An investigation has been made with rocket-propelled models in free flight to determine the external drag and pressure recovery of the NACA 1-40-250 nose inlet at zero angle of attack. The Mach number range of the tests was from 0.9 to 1.8 and the corresponding Reynolds numbers based on body diameter varied from 4,000,000 to 10,000,000. A technique was developed for varying the internal air flow during flight so that the drag and pressure-recovery characteristics were measured as functions of both mass-flow ratio and Mach number. A pointed parabolic-arc body having the same contour as that of the inlet model aft of the inlet region was also tested to serve as a basis for drag comparison.
